%0 Journal Article
%A Tkachenko, Yaroslav V.
%A Kiforenko, Boris N.
%D 2003
%I Begell House
%N 2
%P 16
%R 10.1615/JAutomatInfScien.v35.i2.20
%T Some Optimal Elementary Close to Elliptic Manoeuvres of Spacecrafts with an Engine of Constant Power and Accumulator of Energy
%U http://dl.begellhouse.com/journals/2b6239406278e43e,294589f50feae947,27876bc12497d0b0.html
%V 35
%X We consider the problem of optimization of trajectories, controls and parameters of a propulsion system of a spacecraft, which performs manoeuvre of changing osculating parameters of an elliptic orbit. Spacecraft is equipped with the engine of low thrust with an accumulator of energy, which makes it possible to perform energy redistribution, which is generated by an onboard source of energy according to level of reactive acceleration. This provides achievement of goal of a manoeuvre with maximal value of ratio of a mass of useful load to the initial mass of the spacecraft. We consider a manoeuvre with variation of only one orbital parameter during one rotation around the centre of attraction as the elementary one. We consider motion in the Newtonian central gravity field. Optimization of controls is realized with application of the Pontryagin maximum principle. Linearized motion equations are integrated in elementary functions. Optimization of parameters of the propulsion system is performed numerically. We present results of calculations, which make it possible to estimate effectiveness of inclusion of accumulators of energy into the propulsion system of constant thrust.
%8 2003-02-01